This report presents the results of wind tunnel pressure distribution measurements made on a model of the Boeing supersonic transport configuration during design of the prototype airplanes. This volume contains upper and lower surface chordwise pressure distributions illustrating the effects of nacelles (including various types of simulated engine failure), flaps, spoilers, sideslip and Reynolds number.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9 Volume 8. Wing Chordwise Pressure Distributions, Effects of: Nacelles, Flaps, Spoilers, Sideslip, and Reynolds Number. Part 1
1972
401 pages
Report
Keine Angabe
Englisch
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Varying sweep wings , Jet transport planes , Experimental data , Graphics , Jet engine nacelles , Flaps(Control surfaces) , Spoilers , Sideslip , Reynolds number , Subsonic flow , Transonic flow , Supersonic flow , Angle of attack , Mach number , Wind tunnel models , Airplane models , Design , Jet engines , Failure , Wing body configurations , Interference , Pressure , Load distribution , Leading edge flaps , Trailing edge , Deflection , Roll , Delta wings , Stalling , Flaperons , Sst technology follow on program , Supersonic transports